Turbine engine airfoil with a woven core and woven layer
A gas turbine engine includes a compressor section, combustor section, and turbine section in serial flow arrangement, and defining an engine longitudinal axis. Sets of blades can be rotatably driven about the longitudinal axis in the compressor section and the turbine section, with adjacent vanes provided between sets of blades. The airfoil structure defining one or more of the blades or vanes can include a core structure which includes a woven or foam core, with an exterior woven layer.
1. A gas turbine engine comprising:
a fan section, a compressor section, combustor section, and turbine section in serial flow arrangement, and defining an engine centerline; and
a composite airfoil assembly provided in one of the fan section, the compressor section, or the turbine section, the composite airfoil assembly comprising:
a core defined by a first three-dimensional weave pattern or a first porous foam structure, the core defining a first stiffness;
a woven layer located exterior of the core, the woven layer defined by a second three-dimensional weave pattern, the woven layer defining a second stiffness; and
a laminate skin located exterior of the woven layer, the laminate skin defining a third stiffness;
wherein the second stiffness is between the first stiffness and the third stiffness is defined in at least one direction defining a stiffness transition between the core and the laminate skin.
2. The gas turbine engine of claim 1 wherein the core includes the first three- dimensional weave pattern, and includes a first set of warp fibers and a first set of weft fibers that extend in at least three directions, whereby the three directions define the three dimensions of the first three-dimensional weave pattern.
3. The gas turbine engine of claim 2 wherein the woven layer includes a second set of warp fibers and a second set of weft fibers that are interlaced in three dimensions.
4. The gas turbine engine of claim 3 wherein the woven layer includes a thickness that is at least three times as thick as an individual tow made from at least one of the second set of warp fibers or the second set of weft fibers.
5. The gas turbine engine of claim 1 wherein the first stiffness, the second stiffness, and the third stiffness are different.
6. The gas turbine engine of claim 1 wherein the woven layer fully covers the core.
7. The gas turbine engine of claim 1 wherein the woven layer is formed as an over braid.
8. The gas turbine engine of claim 1 further comprising an outer woven layer located on the laminate skin, wherein the outer woven layer includes a third three-dimensional weave pattern that is different than the first three-dimensional weave pattern and the second three-dimensional weave pattern.
9. The gas turbine engine of claim 8 wherein the third three-dimensional weave pattern includes a braided weave pattern.
10. A core for an airfoil for use in a gas turbine engine, the core comprising:
an interior core including either a first weave pattern or a porous foam pattern, the core defining a first stiffness;
at least one three-dimensional woven layer provided on the interior core, the at least one three-dimensional woven layer defined by a second weave pattern that is different than the first weave pattern and defining a second stiffness; and
a laminate skin provided on the at least one three-dimensional woven layer and defining a third stiffness;
wherein the second stiffness is between the first stiffness and the third stiffness defining a stiffness transition between the core and the laminate skin.
11. The core of claim 10 wherein the interior core is defined by a three-dimensional braided geometry.
12. The core of claim 10 wherein the at least one three- dimensional woven layer comprises an interior three-dimensional woven layer and an exterior three-dimensional woven layer.
13. The core of claim 12 wherein the interior three-dimensional woven layer is provided on the interior core, and the exterior three-dimensional woven layer is provided on the laminate skin.
14. A gas turbine engine comprising:
a fan section, a compressor section, a combustor section, and a turbine section in serial flow arrangement, and defining an engine centerline; and
a composite airfoil assembly rotatable about the engine centerline, the composite airfoil assembly comprising:
a core having a porous geometry or a woven geometry, the core defining a first stiffness;
at least one three-dimensional woven layer located on the core and defining a second stiffness; and
a laminate skin provided exterior of the at least one three-dimensional woven layer and defining a third stiffness;
wherein the second stiffness is between the first stiffness and the third stiffness defining a stiffness transition between the core and the laminate skin.
15. The gas turbine engine of claim 14 wherein the core includes the porous geometry and is a foam core.
16. The gas turbine engine of claim 15 wherein the at least one three-dimensional woven layer includes a set of warp fibers and a set of weft fibers, and wherein the at least one three-dimensional woven layer includes a thickness that is at least three times as thick as an individual tow formed from at least one of the set of warp fibers and the set of weft fibers.
17. The gas turbine engine of claim 15 wherein the at least one three-dimensional woven layer includes at least two three-dimensional woven layers.
18. The gas turbine engine of claim 17 wherein at least one three-dimensional woven layer of the at least two three-dimensional woven layers comprises a three-dimensional braided layer.